Guide vane ring, guide vane, inner ring and turbomachine

Patent metadata

Field	Value
Publication number	US-10364827-B2
Application number	US-201514672333-A
Country	US
Kind code	B2
Filing date	Mar 30, 2015
Priority date	Mar 31, 2014
Publication date	Jul 30, 2019
Grant date	Jul 30, 2019

Abstract

An adjustable guide vane ring of a turbomachine having an inner ring, the guide vanes of which each have a radially inner vane disk with disk thickness increasing in the direction of flow and acting as a bearing pin; a guide vane, as well as an inner ring for such a guide vane ring, as well as a turbomachine are disclosed.

First claim

The invention claimed is:

1. An adjustable guide vane ring of a turbomachine, with a plurality of guide vanes forming a row of guide vanes and with an inner ring for stabilizing the row of guide vanes, wherein the guide vanes each have a radially outer adjusting pin relative to a lengthwise axis of the guide vane ring, the radially outer adjusting pin being adjustable, and wherein the guide vanes, each with a radially inner vane disk, are directly taken up in bearing recesses of the inner ring and being in direct communication with the inner ring with no bushes residing between the radially inner vane disk and the inner ring, wherein the radially inner vane disks have no bearing pin and act as bearing pins, the radially inner vane disks and/or the bearing recesses are coated on their bearing surfaces, and the guide vanes have an overhang on a side of a back edge past the radially inner vane disks, and a radial height of the radially inner vane disks increases downstream of a primary flow and the radial height of the radially inner vane disks upstream is between 15% and 30% of a diameter of the radially inner vane disks.

2. The adjustable guide vane ring according to claim 1 , wherein the radially inner vane disks have a cylindrical bearing surface over their radial height.

3. The adjustable guide vane ring according to claim 1 , wherein the vane disks are distanced from a base of the bearing recesses.

4. The adjustable guide vane ring according to claim 1 , wherein the inner ring is divided axially and has a front ring segment and a back ring segment, in which the bearing recesses are formed as halves in each case.

5. The adjustable guide vane ring according to claim 4 , wherein the ring segments each have at least one flange displaced radially inward relative to the bearing recesses, for joining the segments together.

6. The adjustable guide vane ring according to claim 4 , wherein the back ring segment has downstream an end section directed radially inward from a segment surface on a side of a primary flow.

7. The adjustable guide vane ring according to claim 6 , wherein a radial gap between the end section and an opposite-lying rotor section is closed by a sealing device.

8. The adjustable guide vane ring according to claim 7 , wherein the sealing device is secured in position by a retaining ring disposed on the inner ring.

9. The adjustable guide vane ring according to claim 4 , wherein the front ring segment has an upstream projection for axial overlapping a body section of an upstream row of rotating blades of the turbomachine.

10. The adjustable guide vane ring according to claim 1 , wherein a secondary flow injection extends through the inner ring, this flow exiting from at least several of the vane disks on an intake side and/or a discharge side.

11. The adjustable guide vane ring according to claim 1 , wherein at least several vane disks have a hollow space.

12. The adjustable guide vane ring according to claim 1 , wherein the adjustable guide vane ring is employed in a turbomachine.

Assignees

• MTU Aero Engines AG

Inventors

• Humhauser Werner
• Klingels Hermann

Classifications

• F05D2240/56

  Brush seals · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title